US3493212A - Rotary machine apparatus - Google Patents

Rotary machine apparatus Download PDF

Info

Publication number
US3493212A
US3493212A US739474A US3493212DA US3493212A US 3493212 A US3493212 A US 3493212A US 739474 A US739474 A US 739474A US 3493212D A US3493212D A US 3493212DA US 3493212 A US3493212 A US 3493212A
Authority
US
United States
Prior art keywords
casing
inner casing
rotor
outer casing
turbine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US739474A
Other languages
English (en)
Inventor
Augustine J Scalzo
Andrew Zabrodsky
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
CBS Corp
Original Assignee
Westinghouse Electric Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Westinghouse Electric Corp filed Critical Westinghouse Electric Corp
Application granted granted Critical
Publication of US3493212A publication Critical patent/US3493212A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
    • F04D17/125—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors the casing being vertically split
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
    • F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods

Definitions

  • the invention relates to a machine, such as a turbine or compressor, having inner and outer tubular casings encompassing the rotor and divided along a horizontal plane into upper and lower semi-cylindrical halves.
  • the improvement lies in the provision of means for rollably supporting the inner casing in the lower half of the outer casing, so that, during servicing, after the upper half of the outer casing is removed, the lower half of the inner casing may be readily rolled out of the lower half of the outer casing Without the necessity of removing the rotor.
  • the rollable support means are brought to bear against the outer cylindrical surface of the lower half of the inner casing to permit removal, and at other times are either retracted or removed so that in normal operation the inner casing is irnmovably supported by the outer casing.
  • Axial flow turbines and compressors are typically provided with an inner casing that contain the rows of stationary nozzles for directing the motive fluid past the rotor blading, and the inner casing is disposed within an outer casing structure for many well known reasons.
  • the inner and outer casings are divided into upper and lower halves that are removably joined to each other at suitable horizontal flanges, by bolts.
  • the nozzle rows are also divided into upper and lower semi-circular halves, so that they may be removed with the associated inner casing half as a unit and then removed from the casing for repair or replacement, it required.
  • the lower half of the inner casing has heretofore not been so easily removable, since the rotor is supported in the lower half of the outer casing and interferes with such removal.
  • an arrangement which permits ready removal of the lower half of the inner casing, together with the lower halves of the stationary nozzle rows, without removal of the rotor.
  • the above is attained by providing a roller structure insertable in the lower outer casing and extending into rolla-ble supporting relation with the inner casing, thereby to permit the inner casing to be rolled about its central longitudinal axis to an uppermost position in which it is free of the rotor, at which time it may readily be lifted clear of the outer lower half casing for service and repair.
  • the roller structure includes a pair of rollers displaced about 30 from the vertical centerline of the casing structure and means to jack the rollers in radial direction until they exert a lifting force on the inner casing and space it from the outer casing to a slight degree sufficient to eliminate dragging thereon.
  • the roller structure includes a ice chain-like series of connected rollers insertable between the lower halves of the inner and outer casings, so that the inner lower casing half is freely rotatable in the outer casing and thus rendered removable.
  • FIGURE 1 is a side elevational view of an axial flow gas turbine power plant having the invention incorporated therein;
  • FIG. 2 is a transverse sectional view on a much larger scale, taken on line II-II of FIG. 1;
  • FIG. 3 is a side elevational view of a portion of the structure shown in FIG. 1, on the same scale as FIG. 2, with the upper half of the outer housing removed;
  • FIG. 4 is a transverse sectional view taken on line IV-IV of FIG. 3, showing only the inner and outer casing structure;
  • FIG. 5 is an enlarged detailed sectional view of one of the roller structures shown in FIG. 4;
  • FIG. 6 is a view similar to FIG. 3, but showing another embodiment of the invention.
  • FIG. 7 is a transverse sectional view taken on line VIIVII of FIG. 6.
  • FIG. 1 there is shown a gas turbine power plant or machine 10 of the axial flow type having the invention embodied therein.
  • this machine includes an air compressor section 12, a fuel combustion section 14, a turbine section 16 and an exhaust hood 18.
  • An air inlet casing 20 is provided for directing air to the compressor section 12, as indicated by the arrow 21, and the exhaust 18 is provided for directing the spent combustion gases to atmosphere, as indicated by the arrow 22.
  • the compressor section 12 includes a compressor rotor structure 23 and the turbine section 16 includes a turbine rotor structure 24.
  • the compressor rotor structure 23 is drivenly con nected to the turbine rotor structure 24 by a connecting shaft 25, and the two rotor structures and connecting shaft 25 form a rotor spindle aggregate 27.
  • the rotor spindle 27 is rotatably supported by suitable bearings 28 and 29 at each end.
  • an outer casing structure 32 comprising inlet casing 33, a compressor casing 34, a combustion casing 35 and a turbine casing 36.
  • the above casings are joined to each other and to the inlet casing 20 and the: exhaust hood 18 by suitable bolted peripheral external flanges and are divided into upper and lower casing halves in a horizontal plane coinciding with the central longitudinal axis of the rotor spindle 27, the upper and lower casing halves being joined to each other by suitable bolted horizontal flanges, for expediency in manufacture, assembly and disassembly for service, as known in the art.
  • FIG. 2 is a transverse sectional view of the turbine section 16 and, as illustrated, the outer turbine casing 36 is provided with suitable peripheral flanges 37 for connection to the adjacent casings 18 and 35 (FIG. 1).
  • the turbine casing is also divided into upper and lower halves 36a and 361; along a central horizontal plane and joined to each other along horizontal external flanges 38 by suitable bolts 39.
  • the turbine rotor 24 is provided with one or more annular rows of radially extending blades 40 extending past and cooperatively associated with a like number of annular rows of stationary nozzle blades 41.
  • the stationary nozzle blades 41 are carried by suitable outer shroud rings 42 received in a tubular inner blade ring or casing 43.
  • the shroud rings 42 are divided into upper and lower halves 42a and 42b, and in a like manner, the inner casing 43 is divided into upper and lower halves 43a and 43b and joined together along horizontal flanges 44 by suitable bolts 45.
  • the inner casing 43 is maintained in concentric spaced relation with the outer casing 36 by a plurality of outwardly extending peripheral flanges 47 and 48 (FIGS. 2 and 3) and keyed thereto by a suitable dowel pin 49.
  • the turbine structure is substantially conventional, and for service and repair the upper half of the outer turbine casing 36:: can be readily removed by removing the bolts 39 that join the horizontal flanges 38, and by removing the bolts that join the peripheral flanges 37 to the adjacent casing structure 35 and 18. Access is thus gained to the upper half of the inner turbine casing 43a which can then be removed by removing the bolts 45 that join the horizontal flanges.
  • nozzle blades 41 and the shroud rings 42a in the upper half of the inner casing 43a are carried thereby, they may be removed as a unit and then readily replaced or repaired as required, as known in the art.
  • FIGS. 3 and 4 are views with the upper outer turbine casing half 36a removed and in readiness for removal of the inner casing 43, in accordance with the invention.
  • the lower outer turbine casing half 36b is provided with two apertures 51 disposed in radial alignment with the flange 48 on the inner casing 43.
  • the apertures 51 are angularly displaced with the vertical centerline passing through the center C of the inner casing 43, for example on the order of about 30. However, this angle is not critical and may be considerably greater or less, as desired.
  • a roller structure 52 for insertion in each aperture 51 is provided for attachment to the lower outer casing half 36b.
  • the roller structure 52 includes a mounting plate 53 of cup-shape having a central cavity 54.
  • the cavity 54 is of about the same diameter as that of the mating aperture 51 in the turbine casing half 36b and has received therein a cylindrical block 55.
  • the cylindrical block carries a roller 56 suitably supported therein for rotation by a journal 57 and journal bearings 58,
  • the block 55 is held captive in the cavity 54 and guided for longitudinal movement but restrained against rotative movement by an elongated bolt 60 attached thereto and extending through a clearance hole in the mounting plate.
  • the position of the block 55 is movably adjusted by a jack-screw 61 threadedly received in the plate 53.
  • the plate 53 is bolted to the lower outer casing half 36b by a plurality of bolts 62.
  • roller structures 52 are provided for attachment to the lower outer casing half 36b in alignment with the peripheral flange 47.
  • the upper inner casing half 43a may be readily removed after the outer upper casing half 3612 is removed.
  • the jack screws 61 are then screwed in radially inwardly direction to urge the rollers 56 into forcible abutment with the peripheral flange 48 and such jacking movement is continued until the flange 48 is lifted clear of abutment with the inner surface 63, so that the inner casing 43 is rollably supported by the rollers 56 and freely rotatable relative to the outer lower casing half 36b.
  • the thus repaired inner casing lower half 43a and its nozzle blades may then be re-installed and returned to its original position by reversing the above procedure.
  • roller structures 52 may be removed from the low outer casing half, if desired, and the apertures 51 covered by suitable cover plates (not shown) bolted to the outer casing by the same bolts 62.
  • the preferable and more precise manner of rolling the inner lower casing half 43b to the upper position, in view of its large inertia, is by employment of a pair of chain hoists 64A and 64B.
  • the chain hoists are anchored to the opposing outer lower half casing flanges 38 by suitable eye-bolts 65 and connected to a suitable tab 66 on the upper inner casing half 43a.
  • the inner casing 43 may be rotated with a high degree of precision and control in clockwise direction thereby to bring the lower inner casing half to the top, for removal.
  • the latch plates 68 are bolted to the outer casing flanges 38 by suitable bolts 69 and to the flange 48 of the lower inner casing half 43b, to thereby lock the two lower casing halves together.
  • the upper inner casing half 43a may then be easily disassembled from the lower inner casing half for servicing without disturbing the rotor 24 and may be replaced and restored to its original position by reversing the above steps.
  • FIGS. 6 and 7 are views similar to FIGS. 3 and 4, respectively, showing a second embodiment of the invention.
  • an inner turbine casing 70 divided into upper and lower halves 70a and 70b and joined to each other by horizontal flange structure 72, is disposed within an outer turbine casing divided into a lower half 73b and an identical upper half (not shown).
  • the inner casing halves 70a and 70b are further divided into a plurality (four in the example shown) of blade ring structures 74, 75, 76 and 77 and each of the ring structures is arranged to receive one of the rows of stationary nozzle blades 41 (FIG. 2).
  • the ring structure 4 is provided with a pair of peripheral flanges 78 and 79.
  • the flange 78 in normal operation, is disposed in supporting abutment with an inner annular rib 81 formed in the casing 73b and is provided with an annular recess 82.
  • the flange 79 in normal operation. is disposed in supporting abutment with an annular recess 83 in the casing 73b.
  • the ring structure 74 is provided with a pair of diametrically opposed keys 84 clamped between the mating horizontal flanges 72.
  • the keys 84 are supported on the horizontal flanges 85 of the outer lower casing half 73b and are effective to support the ring structure 74 in a central position with respect to the axis of the turbine rotor (not shown) and to prevent rotary displacement.
  • the recess 83 in the lower outer casing 73b is effective to prevent axial translation of the ring structure 74.
  • the remaining ring structures 75, 76 and 77 are formed and supported in the same manner and need not be further described, except to point out that they are of increasing diameter from left to right to accommodate the larger nozzle blades employed in succeeding motive fluid expansion stages, as known in the art.
  • the ring structures 74, 75, 76 and 77 are disposed in transverse face-to-face sealing abutment with each other but are not joined to each other, therefore they are removable individually.
  • FIGS. 6 and 7 illustrate the ring structures in readiness for removal, with the ring structure 74 in readiness for removal before the others. Accordingly, each of the ring structures 7477, inclusive, has been lifted vertically to a small degree by individual pairs of jack bolts 87, 88, 89 and 90. The jack bolts are received in threaded openings in the keys 84 and bear downwardly against the horizontal flanges 85 to lift their respective ring structures.
  • a first length of roller chain 91 comprising a series of connected rollers (much like a bicycle sprocket chain) is then inserted into the annular space between the peripheral flange 79 and the annular recess 83 through the open end defined thereby at the horizontal flanges 72 and 85 of the inner and outer casings.
  • a second length of roller chain 91 is then inserted into the annular space between the peripheral recess 82 and the lower outer casing rib 81, in a manner similar to the first chain.
  • the two roller chains are fed through the entire lower half of the inner casing as shown in FIG. 2, and then the jack screws 87 are unscrewed from the keys 84, thereby lowering the inner ring structure 74 into supporting abutment with the two roller chains 91.
  • the keys 84 are then removed from the flanges 72, thereby rendering the ring structure 74 rollably supported by the two roller chains 91.
  • the ring structure 74 may then, as in the first embodiment, be rolled about the axis y manually without tools to bring the lower half of the ring structure 74 to a position ,above and out of the outer lower casing half 7015 for removal.
  • rolling may be accomplished by a pair of chain hoists 92 and 93, in the same manner as described in connection with the first embodiment..
  • the lower half of the ring structure 74 may be repositioned in the lower outer casing half 70b by reversing the above procedure and removing the two roller chains 91.
  • the upper ring half may be placed in position and secured to the lower half and to the outer casing by the keys 84.
  • the other ring structures 75, 76 and 77 may be removed in the same manner as described in connection with the ring structure 74.
  • the ring structures 74-77 may be rolled out, as above, in any desired order. Also, only those ring structures which require servicing need be removed with this embodiment. In such event, the jack screws 87, 88, 89 and 90 are only employed in connection with the ring structures that are to be removed.
  • a rotary machine comprising an inner casing structure having an outer peripheral surface portion of circular cross-section, an outer casing structure having an inner peripheral surface portion of circular cross-section, said inner casing being received in said outer casing with its outer surface portion in mating relation with the inner surface portion, said outer casing being divided into upper and lower halves removably joined to each other, said inner casing being divided into upper and lower halves removably joined to each other, and means effective to rollably support said inner casing in said outer casing.
  • the rollable support means is removably associated with the casing structure.
  • the rollable support means comprises a rotatable member, means for rotatably supporting said rotatable member, and means for attaching said supporting means to the lower half of the outer casing with said rotatable member in registry with said aperture and in load supporting relation with the inner casing. 4.
  • outer peripheral surface portion of the inner casing and the inner peripheral surface portion of the outer casing jointly define a peripheral groove, whereby when the upper half of the outer casing is removed from the lower half of the: outer casing the groove is coextensive with the lower half of the easing structures and accessible from diametrically opposed open ends, and means for permitting insertion of the rollable supporting means in the groove through one of said open ends.
  • the means for permitting insertion of the rollable support means includes a pair of jack screws. 7.
  • the rotatable members are rollers and said rollers are connected to each other in a chain.
  • the upper half of the outer casing being removable to expose the inner casing
  • the inner casing being rotatable about the rotor on the roll-ably supporting means to permit removal of the lower half of the inner casing without removing said rotor.
  • the rollable supporting means comprises a rotatable member
  • An axial flow elastic fluid utilizing machine comprising an inner casing structure of annular shape and having an outer peripheral surface portion of circular crosssection;
  • said inner casing structure having a row of stationary blades received therein;
  • an outer casing structure having an inner peripheral surface portion of circular cross-section
  • said inner casing being received in said outer casing with its outer surface portion in mating relation with said inner surface portion;
  • said outer casing being divided into upper and lower halves removably joined to each other;
  • said inner casing being divided into upper and lower halves removably joined to each other;
  • a rotor disposed in said inner casing and having a longitudinal rotational axis
  • said rotor having an annular row of blades disposed about its periphery and operatively associated with the stationary blades of said inner casing structure;
  • the means for permitting insertion of the rollable support means includes a pair of jack screws for lifting and lowering the inner casing relative to the lower half of the outer casing.
  • the rollable supporting means comprises a series of rotatable members disposed in the groove.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US739474A 1968-06-24 1968-06-24 Rotary machine apparatus Expired - Lifetime US3493212A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US73947468A 1968-06-24 1968-06-24

Publications (1)

Publication Number Publication Date
US3493212A true US3493212A (en) 1970-02-03

Family

ID=24972478

Family Applications (1)

Application Number Title Priority Date Filing Date
US739474A Expired - Lifetime US3493212A (en) 1968-06-24 1968-06-24 Rotary machine apparatus

Country Status (7)

Country Link
US (1) US3493212A (de)
CH (1) CH510818A (de)
DE (1) DE1930959C3 (de)
FR (1) FR2011596A1 (de)
GB (1) GB1211313A (de)
NL (1) NL6909136A (de)
SE (1) SE353126B (de)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4648799A (en) * 1981-09-22 1987-03-10 Westinghouse Electric Corp. Cooled combustion turbine blade with retrofit blade seal
US4925363A (en) * 1989-02-13 1990-05-15 Westinghouse Electric Corp. Blade ring rollout roller
US5685693A (en) * 1995-03-31 1997-11-11 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US5971702A (en) * 1998-06-03 1999-10-26 Dresser-Rand Company Adjustable compressor bundle insertion and removal system
US6224332B1 (en) * 1999-05-14 2001-05-01 General Electric Co. Apparatus and methods for installing, removing and adjusting an inner turbine shell section relative to an outer turbine shell section
US20100083499A1 (en) * 2007-10-23 2010-04-08 Mitsubishi Heavy Industries, Ltd. Method for removing blade ring and member for removing blad ring
CN102826441A (zh) * 2011-06-16 2012-12-19 通用电气公司 用于调整壳体中的屏护块的系统和方法
EP2644844A1 (de) 2012-03-30 2013-10-02 Alstom Technology Ltd Gasturbine mit Innengehäuse und Aussengehäuse und Verfahren zum Demontieren der Gehäuse
RU2498089C1 (ru) * 2012-05-22 2013-11-10 Алексей Николаевич Орберг Способ монтажа внутренней вставки корпуса турбины газотурбинного агрегата
US20140026414A1 (en) * 2012-07-26 2014-01-30 General Electric Company Method and system for assembling and disassembling turbomachines
US20140072422A1 (en) * 2012-09-10 2014-03-13 Alstom Technology Ltd. Method and guide for removing an inner casing from a turbomachine
JP2014051985A (ja) * 2012-09-10 2014-03-20 Alstom Technology Ltd 機械から内側ケーシングを取り外す方法
US20150267561A1 (en) * 2014-03-20 2015-09-24 Alstom Technology Ltd Turbomachine and method for disassembling such a turbomachine
JP2018519451A (ja) * 2015-05-07 2018-07-19 ヌオーヴォ・ピニォーネ・テクノロジー・ソチエタ・レスポンサビリタ・リミタータＮｕｏｖｏ Ｐｉｇｎｏｎｅ Ｔｅｃｎｏｌｏｇｉｅ Ｓ．Ｒ．Ｌ． タービン、とくにはガスタービンのバケットの間にノズルを組み込むための方法および装置
US10890196B2 (en) 2013-11-26 2021-01-12 Mitsubishi Power, Ltd. Dummy ring assembly for removing vane segments, and method of removing vane segments using same
CN114526175A (zh) * 2022-04-24 2022-05-24 中国航发四川燃气涡轮研究院 一种用于加力燃烧室的齿轮传动后涵道引射器
US20230066823A1 (en) * 2021-06-04 2023-03-02 Mitsubishi Heavy Industries, Ltd. Turbine casing, gas turbine, and aligning method
WO2023137590A1 (en) * 2022-01-18 2023-07-27 Siemens Energy Global GmbH & Co. KG Rolling device for inner casing part of gas turbine
US11846208B2 (en) * 2021-09-29 2023-12-19 Doosan Enerbility Co., Ltd. Apparatus for disassembling and assembling lower vane carrier and method for disassembling and assembling lower vane carrier using same

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2560854B1 (fr) * 1984-03-07 1986-09-12 Snecma Capotages structuraux participant a la rigidite d'ensemble d'un turboreacteur
US5233822A (en) * 1991-01-31 1993-08-10 General Electric Company Method and system for the disassembly of an annular combustor
DE19719770A1 (de) * 1997-05-10 1998-11-12 Asea Brown Boveri Turbomaschine
WO2006103152A1 (de) * 2005-03-29 2006-10-05 Alstom Technology Ltd Verfahren und vorrichtung zum austausch von bauteilen einer strömungsrotationsmaschine
DE102006004785A1 (de) * 2006-02-02 2007-08-30 Alstom Technology Ltd. Strömungsmaschine
WO2008012195A1 (de) * 2006-07-24 2008-01-31 Siemens Aktiengesellschaft Verfahren zum herausdrehen einer ringhälfte eines insgesamt ringförmigen leitapparats aus einer unteren gehäusehälfte einer axial durchströmbaren, stationären strömungsmaschine, montagevorrichtung, montagevorrichtungsverbund und hilfshalbring hierfür
GB2442238B (en) 2006-09-29 2008-10-01 Rolls Royce Plc Sheet metal blank
GB2445952B (en) 2007-01-25 2011-07-20 Siemens Ag A gas turbine engine
DE102008035427A1 (de) * 2008-07-30 2010-02-04 Man Turbo Ag Strömungsmaschine, Verfahren und Modulsystem zur Herstellung einer solchen Strömungsmaschine
US20130326875A1 (en) * 2012-06-08 2013-12-12 General Electric Company Method and apparatus for roll-in and alignment of a casing shell of a gas turbine
JP6205058B2 (ja) * 2013-12-05 2017-09-27 ゼネラル・エレクトリック・カンパニイ タービンシュラウドブロック取り外し装置
EP2921657A1 (de) * 2014-03-20 2015-09-23 Alstom Technology Ltd Werkzeug zur Demontage des Innengehäuses aus einer Turbomaschine
CN111906494B (zh) * 2019-05-10 2022-05-31 中国航发商用航空发动机有限责任公司 一种装配工装

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1067356A (en) * 1913-03-26 1913-07-15 Ljungstroems Angturbin Ab Steam-turbine.
US2199595A (en) * 1939-05-11 1940-05-07 Murray Iron Works Company Turbine
US2638743A (en) * 1949-04-29 1953-05-19 Ruston & Hornsby Ltd Construction of turbine-inlet and stator elements of gas turbines
GB815032A (en) * 1956-03-27 1959-06-17 Maschf Augsburg Nuernberg Ag Improvements in or relating to multi-stage axial-flow turbines and compressors
FR1182175A (fr) * 1956-09-14 1959-06-23 Licentia Gmbh Enveloppe de turbine axiale
US3066850A (en) * 1961-02-01 1962-12-04 Globe Ind Inc Multistage fan
US3181232A (en) * 1962-03-21 1965-05-04 Atomic Energy Authority Uk Apparatus for replacing an impeller

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1067356A (en) * 1913-03-26 1913-07-15 Ljungstroems Angturbin Ab Steam-turbine.
US2199595A (en) * 1939-05-11 1940-05-07 Murray Iron Works Company Turbine
US2638743A (en) * 1949-04-29 1953-05-19 Ruston & Hornsby Ltd Construction of turbine-inlet and stator elements of gas turbines
GB815032A (en) * 1956-03-27 1959-06-17 Maschf Augsburg Nuernberg Ag Improvements in or relating to multi-stage axial-flow turbines and compressors
FR1182175A (fr) * 1956-09-14 1959-06-23 Licentia Gmbh Enveloppe de turbine axiale
US3066850A (en) * 1961-02-01 1962-12-04 Globe Ind Inc Multistage fan
US3181232A (en) * 1962-03-21 1965-05-04 Atomic Energy Authority Uk Apparatus for replacing an impeller

Cited By (37)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4648799A (en) * 1981-09-22 1987-03-10 Westinghouse Electric Corp. Cooled combustion turbine blade with retrofit blade seal
US4925363A (en) * 1989-02-13 1990-05-15 Westinghouse Electric Corp. Blade ring rollout roller
GB2228051A (en) * 1989-02-13 1990-08-15 Westinghouse Electric Corp Rotary machine casings
FR2643112A1 (fr) * 1989-02-13 1990-08-17 Westinghouse Electric Corp Machine tournante, comme une turbine ou un compresseur, equipee d'une structure de roulement entre les carters interieur et exterieur
GB2228051B (en) * 1989-02-13 1992-12-09 Westinghouse Electric Corp Blade ring rollout roller
US5779442A (en) * 1995-03-31 1998-07-14 General Electric Company Removable inner turbine shell with bucket tip clearance control
US5685693A (en) * 1995-03-31 1997-11-11 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US5906473A (en) * 1995-03-31 1999-05-25 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US5913658A (en) * 1995-03-31 1999-06-22 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US6079943A (en) * 1995-03-31 2000-06-27 General Electric Co. Removable inner turbine shell and bucket tip clearance control
US6082963A (en) * 1995-03-31 2000-07-04 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US5971702A (en) * 1998-06-03 1999-10-26 Dresser-Rand Company Adjustable compressor bundle insertion and removal system
US6224332B1 (en) * 1999-05-14 2001-05-01 General Electric Co. Apparatus and methods for installing, removing and adjusting an inner turbine shell section relative to an outer turbine shell section
US20100083499A1 (en) * 2007-10-23 2010-04-08 Mitsubishi Heavy Industries, Ltd. Method for removing blade ring and member for removing blad ring
US8276273B2 (en) * 2007-10-23 2012-10-02 Mitsubishi Heavy Industries, Ltd. Method for removing blade ring and member for removing blade ring
EP2535530A3 (de) * 2011-06-16 2017-06-07 General Electric Company System und Verfahren zur Anpassung eines Mantelringblocks in einem Gehäuse
CN102826441A (zh) * 2011-06-16 2012-12-19 通用电气公司 用于调整壳体中的屏护块的系统和方法
US20120317772A1 (en) * 2011-06-16 2012-12-20 General Electric Company System and method for adjusting a shroud block in a casing
US8757962B2 (en) * 2011-06-16 2014-06-24 General Electric Company System and method for adjusting a shroud block in a casing
EP2644844A1 (de) 2012-03-30 2013-10-02 Alstom Technology Ltd Gasturbine mit Innengehäuse und Aussengehäuse und Verfahren zum Demontieren der Gehäuse
RU2498089C1 (ru) * 2012-05-22 2013-11-10 Алексей Николаевич Орберг Способ монтажа внутренней вставки корпуса турбины газотурбинного агрегата
US9097123B2 (en) * 2012-07-26 2015-08-04 General Electric Company Method and system for assembling and disassembling turbomachines
US20140026414A1 (en) * 2012-07-26 2014-01-30 General Electric Company Method and system for assembling and disassembling turbomachines
US9528393B2 (en) * 2012-09-10 2016-12-27 General Electric Technology Gmbh Method and guide for removing an inner casing from a turbomachine
US20140072422A1 (en) * 2012-09-10 2014-03-13 Alstom Technology Ltd. Method and guide for removing an inner casing from a turbomachine
KR101557274B1 (ko) 2012-09-10 2015-10-05 알스톰 테크놀러지 리미티드 기계로부터 내부 케이싱 제거 방법
JP2014051985A (ja) * 2012-09-10 2014-03-20 Alstom Technology Ltd 機械から内側ケーシングを取り外す方法
US10890196B2 (en) 2013-11-26 2021-01-12 Mitsubishi Power, Ltd. Dummy ring assembly for removing vane segments, and method of removing vane segments using same
US20150267561A1 (en) * 2014-03-20 2015-09-24 Alstom Technology Ltd Turbomachine and method for disassembling such a turbomachine
US11215079B2 (en) * 2014-03-20 2022-01-04 Ansaldo Energia Switzerland AG Turbomachine and method for disassembling such a turbomachine
JP2018519451A (ja) * 2015-05-07 2018-07-19 ヌオーヴォ・ピニォーネ・テクノロジー・ソチエタ・レスポンサビリタ・リミタータＮｕｏｖｏ Ｐｉｇｎｏｎｅ Ｔｅｃｎｏｌｏｇｉｅ Ｓ．Ｒ．Ｌ． タービン、とくにはガスタービンのバケットの間にノズルを組み込むための方法および装置
US10851674B2 (en) * 2015-05-07 2020-12-01 Nuovo Pignone Tecnologie Srl Method and apparatus for assembling nozzles between buckets of a turbine, particularly a gas turbine
US20230066823A1 (en) * 2021-06-04 2023-03-02 Mitsubishi Heavy Industries, Ltd. Turbine casing, gas turbine, and aligning method
US11661864B2 (en) * 2021-06-04 2023-05-30 Mitsubishi Heavy Industries, Ltd. Turbine casing, gas turbine, and aligning method
US11846208B2 (en) * 2021-09-29 2023-12-19 Doosan Enerbility Co., Ltd. Apparatus for disassembling and assembling lower vane carrier and method for disassembling and assembling lower vane carrier using same
WO2023137590A1 (en) * 2022-01-18 2023-07-27 Siemens Energy Global GmbH & Co. KG Rolling device for inner casing part of gas turbine
CN114526175A (zh) * 2022-04-24 2022-05-24 中国航发四川燃气涡轮研究院 一种用于加力燃烧室的齿轮传动后涵道引射器

Also Published As

Publication number Publication date
CH510818A (de) 1971-07-31
FR2011596A1 (de) 1970-03-06
DE1930959B2 (de) 1977-09-29
NL6909136A (de) 1969-12-30
DE1930959C3 (de) 1978-05-18
DE1930959A1 (de) 1970-01-08
GB1211313A (en) 1970-11-04
SE353126B (de) 1973-01-22

Similar Documents

Publication Publication Date Title
US3493212A (en) Rotary machine apparatus
US3628884A (en) Method and apparatus for supporting an inner casing structure
JP5916889B2 (ja) タービン軸受の取外し方法および取付け方法ならびにこれらの方法を実施するための装置
US5906473A (en) Removable inner turbine shell with bucket tip clearance control
EP2690256B1 (de) Verfahren und System zur Montage und Demontage von Turbomaschinengehäusen
US4925363A (en) Blade ring rollout roller
US3861825A (en) Multistage pump and manufacturing method
US9388709B2 (en) Gas turbine rotor and exhaust maintenance skid
JPH0341641B2 (de)
US5346365A (en) Gas turbine with exhaust gas casing and exhaust gas duct
EP2772617A1 (de) Rotationsströmungsmaschine mit Abstützmitteln und Verfahren zur Demontage der Maschine
EP3009617A1 (de) Vorrichtung zum anheben einer rotierenden welle und verfahren zum anheben einer rotierenden welle
US3366365A (en) Turbines
JP6219129B2 (ja) ガスタービンのタービン区画を組み立て及び分解するためのシステム
RU2280194C1 (ru) Насосный агрегат
US20140356152A1 (en) Apparatus for moving turbine shell
US20240151157A1 (en) Maintenance minimizing turbine apparatus and method therefor
KR200343095Y1 (ko) 발전설비의 로터 축 베어링 점검용 승강장치
US3140821A (en) Gas turbine plant
JPS5925092B2 (ja) タ−ボ機械および静翼組立体をタ−ボ機械内に据付ける方法
JPH0467030B2 (de)
KR100395827B1 (ko) 냉각재 펌프의 축추력 보호기 회전 적재장치
WO2023072354A1 (en) Method for performing maintenance on a yaw system of a wind turbine
US3895887A (en) Gas turbine for use in a closed cycle plant
WO2024094388A1 (en) Disassembly and reassembly of a generator rotor in a plant